Aeroelastic response of a pitch-plunge airfoil with non-zero initial angle of attack

Kód výsledku v IS VaVaI

<a href="https://www.isvavai.cz/riv?ss=detail&h=RIV%2F46747885%3A24220%2F19%3A00006179" target="_blank" >RIV/46747885:24220/19:00006179 - isvavai.cz</a>

Nalezeny alternativní kódy

RIV/46747885:24620/19:00006179

Výsledek na webu

<a href="http://www.fiv2018.com/ocs/index.php/fiv2018/fivcan/paper/view/152" target="_blank" >http://www.fiv2018.com/ocs/index.php/fiv2018/fivcan/paper/view/152</a>

DOI - Digital Object Identifier

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Jazyk výsledku

angličtina

Název v původním jazyce

Aeroelastic response of a pitch-plunge airfoil with non-zero initial angle of attack

Popis výsledku v původním jazyce

Flow-induced vibration of a NACA0015 airfoil model with pitch and plunge degrees of freedom has been studied in a wind tunnel. The model is supported by linear springs and replaceable torsional springs, yielding different pitch-to-plunge natural frequency ratios. The chord length is c = 59.5 mm, the elastic axis is located at c/3. For supercritical inflow velocities, the airfoil undergoes aeroelastic oscillations with relatively large amplitudes both in pitch and plunge. The study reports on vibration and dynamic pressure measurements and Schlieren visualizations of the flow field for the case of non-zero initial angle of attack, compared to previous measurements with zero initial incidence angle. The results suggest that a deep dynamic stall instability with fully separated airflow, which eventually develops for supercritical flow velocities, is initially triggered by a classical coupled-mode flutter instability.

Název v anglickém jazyce

Aeroelastic response of a pitch-plunge airfoil with non-zero initial angle of attack

Popis výsledku anglicky

Flow-induced vibration of a NACA0015 airfoil model with pitch and plunge degrees of freedom has been studied in a wind tunnel. The model is supported by linear springs and replaceable torsional springs, yielding different pitch-to-plunge natural frequency ratios. The chord length is c = 59.5 mm, the elastic axis is located at c/3. For supercritical inflow velocities, the airfoil undergoes aeroelastic oscillations with relatively large amplitudes both in pitch and plunge. The study reports on vibration and dynamic pressure measurements and Schlieren visualizations of the flow field for the case of non-zero initial angle of attack, compared to previous measurements with zero initial incidence angle. The results suggest that a deep dynamic stall instability with fully separated airflow, which eventually develops for supercritical flow velocities, is initially triggered by a classical coupled-mode flutter instability.

Druh

O - Ostatní výsledky

CEP obor

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OECD FORD obor

20304 - Aerospace engineering

Projekt

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Návaznosti

I - Institucionalni podpora na dlouhodoby koncepcni rozvoj vyzkumne organizace

Rok uplatnění

2019

Kód důvěrnosti údajů

S - Úplné a pravdivé údaje o projektu nepodléhají ochraně podle zvláštních právních předpisů